A three-dimensional aerospace panel node edge-reduction structure

Abstract

This application discloses a three-dimensional aviation plate node edge-receiving structure, relating to the field of aviation plate technology, including a wall corner, a clamping component, an aviation plate, a connecting aviation plate, and an abutment component; the clamping component includes a base plate, a clamping plate one, and a clamping plate two; the base plate is set on the wall corner; there are two clamping plates one and two, which correspond one-to-one, and are used to clamp and fix the aviation plate or the connecting aviation plate; clamping plate one is fixed on the base plate, and clamping plate two is fixed on clamping plate one; the abutment component includes an outer expansion plate and a paraffin wax bladder; it enables workers to manually press the outer expansion plate to retract after heating and melting the paraffin wax, thereby enlarging the opening for inserting the aviation plate or the connecting aviation plate on both sides, making it easy to insert the aviation plate or the connecting aviation plate; the paraffin wax gradually solidifies at room temperature, forming a rigid support together with the outer expansion plate; it can be independently disassembled and assembled, and when disassembling a single aviation plate or the connecting aviation plate, the abutment component acts as a physical barrier to prevent adjacent aviation plates or the connecting aviation plate from being disassembled.

Description

Technical Field

[0001] This utility model relates to the field of aviation board technology, and in particular to a three-dimensional aviation board node edge-reducing structure. Background Technology

[0002] Three-dimensional aviation panels, also known as aluminum cone-core aviation panels or three-dimensional aluminum composite panels, are composite panels with aluminum as the core and a sandwich structure design. They are lightweight, high-strength, fire-resistant, earthquake-resistant, easy to process, and corrosion-resistant, and are widely used in building curtain walls, interior decoration, aerospace, and rail transportation.

[0003] Existing technologies have poor edge finishing for aircraft panels, with bolts directly exposed at the edges, resulting in poor aesthetics. Furthermore, while clamping structures hold the panels in place, adjacent panels fit together seamlessly, making individual disassembly impossible. Disassembling a single panel also causes adjacent panels to shift, reducing safety and efficiency. Additionally, the lack of an automatic expansion mechanism during insertion makes insertion difficult, further decreasing work efficiency. Utility Model Content

[0004] This application provides a three-dimensional aviation plate node edge-finishing structure, solving the problems of poor edge-finishing effects in existing technologies, where bolts are directly exposed at the edges, resulting in poor aesthetics. While the clamping structure holds the aviation plates, adjacent plates fit together seamlessly during use, making individual disassembly impossible. Furthermore, disassembling a single plate can cause adjacent plates to shift, reducing safety and efficiency. Additionally, the lack of an automatic expansion structure at the opening makes insertion difficult. The reduced work efficiency allows workers to manually press the outer expansion plate inward after the heated paraffin wax melts, enlarging the opening for inserting the two side aviation plates or connecting aviation plates, making it easy to insert the aviation plates or connecting aviation plates; the paraffin wax gradually solidifies at room temperature, forming a rigid support together with the outer expansion plate; independent assembly and disassembly are possible, and when disassembling a single aviation plate or connecting aviation plate, the contact component acts as a physical barrier, preventing adjacent aviation plates or connecting aviation plates from being removed, reducing auxiliary operation time; when it is necessary to disassemble a single aviation plate or connecting aviation plate, simply melting the paraffin wax bag at the corresponding position can enlarge the opening between the outer expansion plate and the second clamping plate, making it easy to pull out.

[0005] This application provides a three-dimensional aviation board node edge-receiving structure, including a wall corner, a clamping component, an aviation board, a connecting aviation board, and an abutment component;

[0006] The clamping assembly includes a base plate, clamping plate one, and clamping plate two;

[0007] The base plate is set at the external corner of the wall;

[0008] There are two clamps, one for clamp and two for clamp, and they correspond one to one. They are used to clamp and fix the aircraft plate or connect the aircraft plate.

[0009] Clamp one is fixed to the base plate, and clamp two is fixed to clamp one;

[0010] The contact components include an outer expansion plate and a paraffin bladder;

[0011] The abutment component is positioned between the two clamps.

[0012] There are two expansion plates, symmetrically arranged, and the expansion plates are rotatably connected to the base plate. A torsion spring is installed at the rotatable connection. In the initial state, the torsion spring makes the two expansion plates open.

[0013] A paraffin bag is fixed between the two outer expansion plates.

[0014] As an improvement, the three-dimensional aerospace panel node edge-closing structure also includes a keel frame and bolts;

[0015] The keel frame is installed on the external corner of the wall using bolts;

[0016] There are two keel frames, which are set on both sides of the external corner of the wall.

[0017] As an improvement, the clamping assembly also includes bolt two;

[0018] The base plate is mounted on the keel frame using two bolts.

[0019] There are two clamping components, which are respectively installed on two keel frames;

[0020] The first clamp has an arc-shaped cross-section and is elastic, while the second clamp is fixed to the side of the first clamp away from the bottom plate.

[0021] The clamping plate is elastically abutting against or connecting to the aircraft plate.

[0022] As an improvement, the number of opposing components is the same as the number of clamping components, and they correspond one-to-one;

[0023] The two ends of the torsion spring on the rotating shaft connecting the outer expansion plate and the base plate are respectively fixed to the outer expansion plate and the base plate;

[0024] The length direction of the outer expansion plate is parallel to the length direction of the second clamping plate, and the rotation axis of the outer expansion plate is parallel to the length direction of the second clamping plate;

[0025] The paraffin capsule is filled with paraffin wax;

[0026] The outer expansion plate is used to abut against or connect to the aviation plate.

[0027] As an improvement, the aviation plate or connecting aviation plate is inserted between the clamping plate two and the outer expansion plate;

[0028] The contact components are located between two adjacent aviation plates or between an aviation plate and a connecting aviation plate;

[0029] The two connecting aviation panels at the top corner of the wall are in contact with each other.

[0030] As an improvement, the melting point of the paraffin inside the paraffin capsule is 45°C to 70°C.

[0031] As an improvement, the impact assembly also includes a bursting chamber and a fracture surface;

[0032] There are two bursting chambers, located on opposite sides of the two outer expansion plates, and the bursting chambers are fixed to the base plate.

[0033] The burst chamber is filled with water-based hot melt adhesive;

[0034] The burst capsule has a fracture.

[0035] When the bursting chamber is compressed, the fracture point ruptures, causing the internal water-based hot melt adhesive to spray out.

[0036] One or more technical solutions provided in the embodiments of this application have at least the following technical effects or advantages:

[0037] Firstly, after the paraffin wax is heated and melted, workers can manually press the outer expansion plate inward to enlarge the opening for inserting the two side aviation plates or connecting aviation plates, making it easy to insert the aviation plates or connecting aviation plates. The paraffin wax gradually solidifies at room temperature, forming a rigid support together with the outer expansion plate. Independent assembly and disassembly are possible. When disassembling a single aviation plate or connecting aviation plate, the contact component acts as a physical barrier to prevent adjacent aviation plates or connecting aviation plates from being removed, reducing auxiliary operation time. When it is necessary to disassemble a single aviation plate or connecting aviation plate, simply melt the paraffin wax bag at the corresponding position to enlarge the opening between the outer expansion plate and the clamping plate, making it easy to pull it out.

[0038] Secondly, the bursting chamber can serve as a warning, with an audible alert indicating to workers that the installation depth limit has been reached, preventing excessive pressure from damaging the aircraft panel or connecting aircraft panels; the water-based hot melt adhesive significantly increases friction after curing, preventing the aircraft panel or connecting aircraft panels from shifting under wind pressure or vibration; the water-based hot melt adhesive evenly disperses the stress on the board, reducing the risk of local deformation, preventing moisture from corroding the internal keel frame and bolts, and reducing the risk of rust. Attached Figure Description

[0039] Figure 1 This is a front sectional view of a three-dimensional aviation plate node edge-receiving structure according to this utility model;

[0040] Figure 2This is a structural diagram of a clamping component for a three-dimensional aviation board node edge-receiving structure according to this utility model;

[0041] Figure 3 This is a schematic diagram of the mounting structure of the contact component of a three-dimensional aviation board node edge-receiving structure according to this utility model;

[0042] Figure 4 This is a schematic diagram of the installation of an aviation plate and a connecting aviation plate according to a three-dimensional aviation plate node edge-reducing structure of this utility model;

[0043] Figure 5 This is a schematic diagram showing the two outward expansion plates of a three-dimensional aviation plate node edge-retracting structure of the present invention approaching each other;

[0044] Figure 6 This is a schematic diagram of the installation of a burst bladder for a three-dimensional aviation plate node edge-receiving structure according to this utility model;

[0045] Figure 7 This is a schematic diagram showing the fracture opening of a three-dimensional aviation plate node edge-receiving structure according to this utility model.

[0046] In the diagram: 100, external corner of the wall; 200, keel frame; 300, clamping assembly; 310, base plate; 320, bolt two; 330, clamping plate one; 340, clamping plate two; 400, bolt one; 500, aviation plate; 600, connecting aviation plate; 700, contact assembly; 710, outward expansion plate; 720, paraffin bag; 730, bursting bag; 740, fracture point. Detailed Implementation

[0047] To facilitate understanding of this utility model, a more comprehensive description of this application will be given below with reference to the accompanying drawings, which show preferred embodiments of the utility model. However, the utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to enable a more thorough and complete understanding of the disclosure of this utility model.

[0048] It should be noted that the terms "vertical," "horizontal," "up," "down," "left," "right," and similar expressions used in this article are for illustrative purposes only and do not represent the only possible implementation.

[0049] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains; the terminology used herein in the description of this invention is for the purpose of describing particular embodiments only and is not intended to limit the invention; the term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0050] Example 1: As Figures 1-5 As shown, this application discloses a three-dimensional aviation plate node edge-receiving structure, including a wall corner 100, a keel frame 200, a clamping component 300, a bolt 400, an aviation plate 500, a connecting aviation plate 600, and an abutment component 700.

[0051] The clamping assembly 300 includes a base plate 310, a first clamping plate 330, and a second clamping plate 340;

[0052] The base plate 310 is set on the external corner of the wall 100;

[0053] There are two clamping plates 330 and 340, and they correspond one to one. They are used to clamp and fix the aviation plate 500 or connect the aviation plate 600.

[0054] Clamp 1 330 is fixed to base plate 310, and clamp 2 340 is fixed to clamp 1 330;

[0055] The abutment component 700 includes an outer expansion plate 710 and a paraffin capsule 720;

[0056] The abutting component 700 is disposed between the two clamping plates 330. The number of abutting components 700 is the same as the number of clamping components 300, and they correspond one-to-one.

[0057] There are two outer expansion plates 710, which are symmetrically arranged. The outer expansion plates 710 are rotatably connected to the base plate 310, and a torsion spring is provided at the rotatable connection. In the initial state, the torsion spring makes the two outer expansion plates 710 open.

[0058] The two ends of the torsion spring on the rotating shaft connecting the outer expansion plate 710 and the base plate 310 are respectively fixed on the outer expansion plate 710 and the base plate 310;

[0059] A paraffin bladder 720 is fixed between two outer expansion plates 710. The paraffin bladder 720 is filled with paraffin wax, and the melting point of the paraffin wax in the paraffin bladder 720 is 45℃ to 70℃.

[0060] The outer expansion plate 710 is used to abut against the aviation plate 500 or to connect the aviation plate 600.

[0061] Specifically, before installing the aviation plate 500 or connecting the aviation plate 600, the paraffin inside the paraffin bag 720 needs to be heated to melt it and cause it to deform. This melting can be achieved using hot air from a blower. The position of the outer expansion plate 710 is manually adjusted so that the aviation plate 500 or connecting the aviation plate 600 can be inserted between the outer expansion plate 710 and the clamping plate 340. Manually adjusting the outer expansion plates 710 brings them closer together, causing the paraffin bag 720 to deform, thereby increasing the distance between the two outer expansion plates 710 and the clamping plate 340, facilitating the insertion of the aviation plate 500 or connecting the aviation plate 600. The outer expansion plate 500 is then inserted by rotating the torsion spring at the connection point. Plate 710 abuts against the aircraft plate 500 or the connecting aircraft plate 600, fixing the position of the aircraft plate 500 or the connecting aircraft plate 600. After the paraffin capsule 720 solidifies, it can improve the position of the aircraft plate 500 or the connecting aircraft plate 600. When it is necessary to disassemble the aircraft plate 500 or the connecting aircraft plate 600, since the abutting component 700 has a separating function, the aircraft plate 500 or the connecting aircraft plate 600 on the other side can be unaffected, and there is no need to fix the plate on the other side by hand. Furthermore, by simply melting the paraffin capsule 720 at the corresponding position, the size of the opening between the outer expansion plate 710 and the clamping plate 340 can be enlarged, making it easier to pull out.

[0062] The keel frame 200 is installed on the external corner 100 of the wall using bolts 400;

[0063] There are two 200mm keel frames, which are set on both sides of the 100mm external corner of the wall.

[0064] The clamping assembly 300 also includes bolt 320;

[0065] The base plate 310 is mounted on the keel frame 200 by bolts 320;

[0066] Specifically, the positions of bolt 400 and bolt 320 are adjusted according to requirements to fix the positions of the keel frame 200 and the base plate 310.

[0067] There are two clamping components 300, which are respectively installed on two keel frames 200;

[0068] The first clamp 330 has an arc-shaped cross section and is elastic, and the second clamp 340 is fixed on the side of the first clamp 330 away from the bottom plate 310;

[0069] The clamp 330 is elastically abutted against the aircraft plate 500 or connected to the aircraft plate 600.

[0070] The length direction of the outer expansion plate 710 is parallel to the length direction of the clamping plate 340, and the rotation axis of the outer expansion plate 710 is parallel to the length direction of the clamping plate 340.

[0071] The aviation plate 500 or connecting aviation plate 600 is inserted between the clamping plate 340 and the outer expansion plate 710;

[0072] The abutting component 700 is located between two adjacent aviation plates 500 or between aviation plate 500 and connecting aviation plate 600;

[0073] Specifically, the two connecting aviation plates 600 at the top corner of the wall 100mm abut against each other to avoid affecting the aesthetics; and the two connecting aviation plates 600 at the corner abut against each other to reduce the existence of edge gaps.

[0074] The technical solutions described in the embodiments of this application have at least the following technical effects or advantages:

[0075] After the paraffin wax is heated and melted, workers can manually press the outward expansion plate 710 to retract it, thus enlarging the opening for inserting the two side aviation plates 500 or connecting aviation plates 600, making it easy to insert the aviation plates 500 or connecting aviation plates 600. The paraffin wax gradually solidifies at room temperature, forming a rigid support together with the outward expansion plate 710. When disassembling a single aviation plate 500 or connecting aviation plate 600, the contact component 700 acts as a physical barrier, preventing adjacent aviation plates 500 or connecting aviation plates 600 from being disassembled, reducing auxiliary operation time. When it is necessary to disassemble a single aviation plate 500 or connecting aviation plate 600, simply melt the paraffin wax bladder 720 at the corresponding position to enlarge the opening between the outward expansion plate 710 and the clamping plate 340, making it easy to pull out.

[0076] Example 2: In the above embodiment, the position of the aircraft plate 500 or connecting aircraft plate 600 is fixed by inserting it between the clamping plate 340 and the outer expansion plate 710. However, during the insertion process, the worker cannot control the insertion force or know the insertion depth at all times, which leads to damage to the aircraft plate 500 or connecting aircraft plate 600 when the pressing pressure is too high. Furthermore, the above embodiment has a poor fixing effect on the aircraft plate 500 or connecting aircraft plate 600. Therefore, the solution of Example 1 is improved, such as... Figures 6-7 As shown:

[0077] The impact component 700 also includes a bursting chamber 730 and a fracture surface 740;

[0078] There are two bursting capsules 730, which are located on opposite sides of the two outer expansion plates 710, and the bursting capsules 730 are fixed on the base plate 310.

[0079] The burst capsule 730 is filled with water-based hot melt adhesive;

[0080] Specifically, when the water-based hot melt adhesive is inside the bursting capsule 730, it is in a liquid state. After being exposed to air for a long time, the adhesive will solidify.

[0081] Water-based hot melt adhesives are existing technology and will not be discussed further here.

[0082] The burst capsule 730 has a fracture opening 740;

[0083] When the bursting bladder 730 is compressed, the fracture point 740 ruptures, causing the internal water-based hot melt adhesive to spray out.

[0084] Specifically, when the worker presses the aircraft plate 500 or the connecting aircraft plate 600, pressing to the deepest point, reaching the bursting bladder 730, the fracture point 740 breaks under pressure when the pressure reaches a certain level, causing the water-based hot melt adhesive stored inside to spray out in all directions. The spraying of the water-based hot melt adhesive produces a hissing sound, alerting the worker that the pressing is nearing completion. The sound disappears after the deepest point has been reached. The water-based hot melt adhesive solidifies after being exposed to air for a period of time, securing the aircraft plate 500 or the connecting aircraft plate 600 in place. When it is necessary to disassemble or replace the aircraft plate 500 or the connecting aircraft plate 600, a blower is used to heat the connection point, melting the water-based hot melt adhesive. The remaining water-based hot melt adhesive then wraps around the new aircraft plate 500 or the connecting aircraft plate 600, securing its position. If there is insufficient water-based hot melt adhesive remaining inside, it can be manually added again to ensure the stability of the fixation.

[0085] The technical solutions described in the embodiments of this application have at least the following technical effects or advantages:

[0086] The bursting chamber 730 serves as an indicator, providing an audible warning to workers that the installation depth limit has been reached, preventing excessive pressure that could damage the aircraft panel 500 or the connecting aircraft panel 600. The water-based hot melt adhesive, after curing, significantly increases friction, preventing the aircraft panel 500 or the connecting aircraft panel 600 from shifting under wind pressure or vibration. The water-based hot melt adhesive also evenly disperses the stress on the panels, reducing the risk of localized deformation and preventing moisture from corroding the internal keel frame 200 and bolts 400, thus reducing the risk of rust.

[0087] The above description is merely a preferred embodiment of this utility model and is not intended to limit the scope of this utility model. For those skilled in the art, various modifications and variations are possible with this utility model. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A three-dimensional air panel node edge-closing structure, characterized by, Includes a wall corner (100), a clamping assembly (300), an aviation plate (500), a connecting aviation plate (600), and an abutment assembly (700); The clamping assembly (300) includes a base plate (310), a first clamping plate (330), and a second clamping plate (340); The base plate (310) is set on the external corner (100) of the wall; There are two clamping plates (330) and two clamping plates (340) respectively, and they correspond one to one. They are used to clamp and fix the aircraft plate (500) or connect the aircraft plate (600). Clamp 1 (330) is fixed on base plate (310), and clamp 2 (340) is fixed on clamp 1 (330); The abutment component (700) includes an outer expansion plate (710) and a paraffin capsule (720); The abutment component (700) is disposed between the two clamps (330); There are two outer expansion plates (710), which are symmetrically arranged. The outer expansion plates (710) are rotatably connected to the base plate (310), and a torsion spring is provided at the rotatable connection. In the initial state, the torsion spring makes the two outer expansion plates (710) open. A paraffin bag (720) is fixed between the two outer expansion plates (710).

2. A three-dimensional aerospace panel node edge-closing structure as claimed in claim 1, characterized in that, The three-dimensional aerospace plate node edge-sealing structure also includes a keel frame (200) and bolts (400); The keel frame (200) is installed on the external corner (100) of the wall by bolt one (400); There are two keel frames (200), which are set on both sides of the external corner of the wall (100).

3. The three-dimensional aerospace panel node edge-closing structure of claim 1, wherein, The clamping assembly (300) also includes bolt two (320); The base plate (310) is mounted on the keel frame (200) by bolts two (320); There are two clamping components (300), which are respectively mounted on two keel frames (200); The first clamp (330) has an arc-shaped cross section and is elastic, and the second clamp (340) is fixed on the side of the first clamp (330) away from the bottom plate (310); The clamp (330) is elastically abutted against the aircraft plate (500) or connected to the aircraft plate (600).

4. The three-dimensional aerospace panel node edge-closing structure of claim 1, wherein, The number of the contacting components (700) is the same as the number of the clamping components (300), and they correspond one-to-one. The two ends of the torsion spring on the rotating shaft connecting the outer expansion plate (710) and the base plate (310) are respectively fixed on the outer expansion plate (710) and the base plate (310); The length direction of the outer expansion plate (710) is parallel to the length direction of the second clamping plate (340), and the rotation axis of the outer expansion plate (710) is parallel to the length direction of the second clamping plate (340); The paraffin capsule (720) is filled with paraffin wax; The expansion plate (710) is used to abut against the aircraft plate (500) or to connect the aircraft plate (600).

5. A three-dimensional aerospace panel node edging structure as defined in claim 4, wherein, The aviation plate (500) or connecting aviation plate (600) is inserted between the clamping plate two (340) and the outer expansion plate (710); The abutting component (700) is located between two adjacent aircraft plates (500) or between an aircraft plate (500) and a connecting aircraft plate (600); The two connecting aviation plates (600) at the top corner of the wall (100) abut against each other.

6. The three-dimensional aerospace panel node edge-reducing structure as described in claim 4, characterized in that, The melting point of the paraffin inside the paraffin bag (720) is 45°C to 70°C.

7. A three-dimensional aerospace panel node edge-closing structure as defined in claim 1, wherein, The impact assembly (700) also includes a burst capsule (730) and a fracture surface (740); There are two bursting capsules (730), which are located on opposite sides of the two outer expansion plates (710) and are fixed to the base plate (310). The burst capsule (730) is filled with water-based hot melt adhesive; The burst capsule (730) has a fracture (740); When the bursting bladder (730) is compressed, the fracture point (740) ruptures, causing the internal water-based hot melt adhesive to spray out.

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